Fuel Management System SC12 SERIES

Transcription

Fuel Management System
SC12 SERIES
Includes PC910 / 920 Supplement
Installation and Maintenance Manual
Senior Aerospace Ketema
790 Greenfield Drive
El Cajon California 92021
619-442-3451 or 619-588-3373
Fax 619-440-1456 or 619-588-3381
www.sfketema .com
SC12 GENERAL INSTRUCTIONS
•
Senior Aerospace Ketema designs, manufactures, and tests its products to meet many
national and international standards. However, for these products to operate within their
normal specifications, you must properly install, use and maintain these products. The
following must be adhered to and integrated with your safety program when installing, using,
and maintaining Senior Aerospace Ketema products.
•
Read and save all instructions prior to installing and operating the product.
•
If you do not understand any of the instructions, contact your Senior Aerospace Ketema
representative for clarification.
•
Follow all warnings, cautions, and instructions marked on and supplied with the product.
•
Inform and educate your personnel in the proper installation and operation of the product.
• Install your equipment as specified in Senior Aerospace Ketema installation instructions and per
applicable local/national codes. Connect all products to the proper electrical sources.
•
Handle, move, and install each product using the appropriate number of personnel and
equipment. Failure to do so could cause serious personal injury.
• To ensure proper performance, use qualified personnel to install and maintain the
product.
•
Equipment contains no user serviceable parts.
•
When repair is required, ensure that the unit is sent to Senior Aerospace Ketema. For repair.
• WARNING This equipment may contain static sensitive devices. Failure to comply with
the proper handling procedures may result in damage to the equipment. Unauthorized
substitutions may result in fire, electrical shock, other hazards, or improper equipment
operation.
•
Ensure that all equipment doors are closed and protective covers are in place, except when
maintenance is being performed by qualified personnel, to prevent electrical shock and
personal injury.
FUEL MANAGEMENT SYSTEM
SC12 SERIES
INSTALLATION AND MAINTENANCE MANUAL
619-442-3451 or 619-588-3373
Fax 619-440-1456 or 619-588-3381
www.sfketema .com
Revision History
Rev
A
B
C
D
E
Issue Date
1983
1990
1998
2000
2001
Date Inserted
By
2 Feb 1983
1 Dec 1990
18 Feb 1998
5 Jan 2000
5 Jan 2001
KK
RWG
RWG
RWG
Retain this record in front of manual.
On receipt of revisions, insert revised pages in the manual and enter revision number, date inserted, and
initials.
GENERAL CONDITIONS OF SALE FOR INSTRUMENTS AND PARTS
The conditions of sale stated herein shall be an integral part of any contract resulting from a purchase order placed upon Senior Aerospace Ketema, and hereinafter called
KETEMA. Any statement made on any form issued by Purchaser shall not operate to defeat the intent of these conditions unless specifically agreed upon in writing by KETEMA.
CONDITIONS OF SALE:
1.
ACCEPTANCE: All orders are subject to an authorized employee of KETEMA at its
principal office.
2.
PRICES: All prices pertaining to an order are quoted in the offering or will be quoted
and confirmed by KETEMA in subsequent addenda thereto.
A.
FIRM OFFER: Except as otherwise provided in the offering, all quoted prices
are firm for thirty (30) days from date of offering. All prices are f.o.b. Shipping
Point (transportation charges collect) unless expressly stated otherwise in the
offering or agreed upon in writing by KETEMA.
B.
TAXES AND OTHER CHARGES: All quoted prices are subject to additions
which may be necessary to cover any duty, tax or charge, now existing or
hereafter imposed by Government authorities upon equipment or services
quoted by KETEMA, or upon the production, sale, distribution, delivery, import
or export thereof, or upon other features related thereof; AND unless otherwise
stated in the offering, prices not quoted in United States currency are based on
the rates of exchange between the U.S. dollar and the quoted currency ruling at
the date of offering and any variation greater than two per centum (2%)
between such rates ruling at the date of offering and date of payment to
KETEMA shall be for the Purchaser's account.
C.
ERRORS: KETEMA reserves the right to correct all typographical or clerical
errors or omissions which may be present in its prices or specifications.
D.
ESCALATION: All prices quoted are based on deliveries as defined in the
offering. KETEMA reserves the right to make partial deliveries of equipment as
it becomes available, unless specified otherwise in the offering or agreed upon
in writing by KETEMA. Delays caused by KETEMA beyond the Quoted Delivery
shall not be subject to escalation. Delays and/or Scope Changes (in
accordance with paragraph 4) caused by Purchaser shall be subject to
escalation at a rate to be determined for each month in excess of the Quoted
Delivery.
E.
RESALE PRODUCTS: KETEMA does not offer price protection on resale
products other than those contained in the KETEMA Price Book. Such products
are quoted subject to price changes from the KETEMA suppliers between the
dale of the offering and the date of the KETEMA invoice.
F.
MAINTENANCE AND SPARE PARTS: Maintenance service and spare parts
are riot included in the price of the product unless specified otherwise in the
offering or agreed upon in writing by KETEMA. Orders for parts or repairs shall
be subject to a minimum billing charge.
3.
PAYMENT TERMS: Payment shall be made within thirty (30) days from the date of the
invoice unless KETEMA specifies an irrevocable letter of credit in a specific currency
placed on a specific bank. Partial payments shall be provided when so specified by
KETEMA or as a result of Scope Changes (in accordance with paragraph 4) in which
event KETEMA shall notify Purchaser in writing of the modified payment terms.
4.
SCOPE CHANGES: All changes affecting the equipment configuration or otherwise
affecting the scope of the order are to be documented in writing for approval and
authorization to incorporate such changes into the order. All changes authorized by
Purchaser are binding only it accepted by KETEMA, and may result in price, delivery,
and/or condition changes. Pricing of changes shall be based on the then current prices.
If an extension of delivery is required beyond the original schedule, escalation shall be
agreed. Letter(s) of credit, if applicable, shall be extended and the values enhanced as
necessary to reflect changes in price and payment arrangements.
S.
CANCELLATION: Purchaser may cancel his order by written notice provided Purchaser
pays cancellation charges on the basis of the percentage of work and/or materials
completed on the date cancellation notice is received by KETEMA. Standard
cancellation/restocking charges are published for standard instruments and such
charges are available from KETEMA upon request. Resale products committed by
KETEMA shall be paid for in full.
6.
TESTING: Any additional tests or inspections requested by Purchaser beyond KETEMA
standard manufacturing procedures shall be for the Purchaser's account, unless
specified otherwise in the offering or agreed upon in writing by KETEMA.
7.
ON-SITE RECEIPT OF EQUIPMENT AND INSTALLATION: Purchaser shall be
responsible for receiving, installing, starting up, and maintaining all equipment, unless
specified otherwise in the offering or agreed upon in writing by KETEMA.
8.
DELIVERY: Title to the equipment and risk of loss or damage shall pass upon delivery
by KETEMA to the possession of the carrier unless specified otherwise in the offering or
agreed upon in writing by KETEMA. Any claims for loss or damage after risk of loss has
passed shall be filed by Purchaser with carrier. KETEMA shall not be liable for loss or
damage from delay in delivery or failure to manufacture. Delivery dates are
approximate and are based on prompt receipt by KETEMA at its factory of all necessary
information including final agreement on detailed specifications, on such date or with
such lead times as may be specified by KETEMA. If delivery is delayed at the request
of, or due to acts or omissions by Purchaser, KETEMA shall have the right to store the
goods at a place of its own choice for Purchaser's account and risk and to invoice
Purchaser in accordance with the original contractual terms and for such storage
charges incurred as a result of the delay.
9.
DOCUMENTATION: KETEMA will provide Purchaser with up to the following quantifies
of applicable standard Drawings and instructions unless specified otherwise in the
offering or agreed upon in writing by KETEMA. Additional copies will be furnished at
extra charge. All documentation will be in the English language unless expressly stated
otherwise in the offering or agreed upon in writing by KETEMA.
A.
DRAWINGS: Two prints or one print plus a sepia reproducible for installation
and maintenance and two prints plus a sepia reproducible for approval, when
applicable. Drawings for resale products shall be those provided by KETEMA
suppliers.
B.
INSTRUCTIONS: Two sets of standard instructions for installation, operation,
and maintenance for standard products; one set for Resale Products and Parts,
all as defined by KETEMA.
10.
SPARE PARTS AVAILABILITY:
A.
ACTIVE PRODUCTS: On all standard KETEMA products, it is KETEMA
policy to provide functionally interchangeable replacement parts during the
period of lime that the product is offered for sale. On Resale Products, no
future availability of spare parts or products is guaranteed,
S.
PRODUCTS WITHDRAWN FROM SALE: It is KETEMA policy that
functionally interchangeable replacement parts for standard noncomputer
products will be available for at least five (5) years from the date of
withdrawal from sale.
11.
12.
13.
14.
15.
WARRANTIES: KETEMA EXPRESSLY WARRANTS THE PRODUCTS
MANUFACTURED BY IT AS MEETING THE APPLICABLE KETEMA PRODUCT
SPECIFICATIONS. KETEMA MAKES NO OTHER WARRANTIES EITHER
EXPRESS OR IMPLIED (INCLUDING WITHOUT LIMITATION WARRANTIES AS TO
THE MERCHANTABILITY OR FITNESS FOR A PARTICULAR PURPOSE).
PURCHASER RETAINS RESPONSIBILITY FOR THE APPLICATION AND
FUNCTIONAL ADEQUACY OF THE OFFERING. IN ADDITION, THE FOLLOWING
SHALL CONSTITUTE THE EXCLUSIVE REMEDIES FOR ANY BREACH BY
KETEMA OF ITS WARRANTIES HEREUNDER.
A.
MATERIAL AND WORKMANSHIP: KETEMA warrants to Purchaser that all
products manufactured by KETEMA shall be free from defects in material and
workmanship, and agrees to either replace or repair free of charge, any such
product, component, or part thereof which shall be returned to the nearest
authorized KETEMA repair facility within one (1) year from the date of
delivery, transportation charges prepaid for the account of Purchaser, The
cost of demonstrating the need to diagnose such defects at the job site, if
required, shall be for the account of the Purchaser. Any product or
component, or part thereof, so replaced or repaired shall be warranted by
KETEMA for the remainder of the original warranty period. Any and all such
replacements or repairs necessitated by inadequacy, preventative
maintenance, or by normal wear and usage, or by the fault of the Purchaser or
power sources supplied by others or by attack and deterioration under
unsuitable environmental conditions shall be for the account of the Purchaser.
KETEMA shall not be obligated to pay any costs or charges including 'back
charges" incurred by the Purchaser or any other party except as may be
agreed upon in writing in advance by KETEMA.
B.
RESALE PRODUCTS: Resale products shall carry only the warranty offered
by the original manufacturer, unless specified otherwise in the offering or
agreed upon in writing by KETEMA. KETEMA shall have no responsibility for
the functioning of resale products specified by Purchaser or his agent.
C.
PATENTS: KETEMA shall defend Purchaser and pay any award of damages
assessed against Purchaser in any suit or proceeding so far as same is based
on any claim that the equipment or any part thereof furnished hereunder
(except for equipment basically of Purchaser's specifications) shall in design
or construction infringe any patent of the country of its manufacture, provided
Purchaser gives KETEMA prompt notice in writing of such claim and permits
KETEMA to contest same through its counsel or, at its option, to settle by
securing for Purchaser the right to continue to use such equipment or by
modifying it to avoid infringement, or by reclaiming it and reimbursing
Purchaser the sum paid therefor; and provided Purchaser gives KETEMA all
necessary authority and assistance, at the expense of KETEMA, to enable
KETEMA to do so.
D.
PARTS: The warranties specified in paragraph 11 A are modified to three (3)
months in the case of parts.
FORCE MAJEURE: Neither party shall be considered in default in performance of
obligations hereunder to the extent that performance of such obligations, or any of
them, is affected by Force Majeure. Force Majeure shall include, but not be limited to,
hostilities, restraint of rulers or peoples, revolution, civil commotion, strike, epidemic,
accident, fire, flood, wind, earthquake, explosion, blockade, or embargo, lack of or
failure of transportation facilities or any law, proclamation, regulation or ordinance,
demand or requirement of any Government or Governmental agency having or
claiming to have jurisdiction over the work or with respect to materials purchased for
the work, or over the parties hereto, or any Act of God, or other act of Government, or
any cause whether of the same or different nature existing or future, which is beyond
the control and without the fault or negligence of the parties hereto.
INSURANCE INDEMNITY: KETEMA will at Purchaser's request submit Certificates of
insurance from Sureties chosen by KETEMA showing the limits of coverage.
KETEMA agrees to indemnity and save harmless Purchaser only against liability
imposed on Purchaser by law with respect to bodily injury or property damage to the
extent such liability results from the performance of KETEMA under this contract.
KETEMA does not agree to indemnity and save Purchaser harmless except as set
forth herein. Purchaser agrees to indemnity and save harmless KETEMA for all loss,
cost or damage incurred by KETEMA as a result of Purchaser's or third parties misuse
or misapplication of KETEMA supplied products. IN NO EVENT, REGARDLESS OF
CAUSE, SHALL KETEMA BE LIABLE FOR INCIDENTAL OR CONSEQUENTIAL
DAMAGE EITHER REAL OR ALLEGED.
MISCELLANEOUS: The validity, construction, and Intrepretation of these conditions
or of any contract of sale including these conditions, and the rights and duties of the
parties thereto, shall be governed by the laws pertaining to KETEMA in its country of
domicile, notwithstanding the inclusion of any services in such contract. Any offering
or contract of which these conditions are a part constitutes the final complete and
exclusive statement of representations made by KETEMA, and KETEMA shall not be
bound by any representations, promises or inducement of any kind unless set forth
herein nor shall be bound to any representations made herein except to the
designated recipient of any offering or contractual commitment. No waiver, alteration
or modification of any of the provisions herein or of the provisions of any contract
arising herefrom shall be binding on KETEMA unless in writing and signed by
Purchaser and KETEMA.
“Seller hereby certifies that these goods were produced in compliance with all
applicable requirements of Section 6, 7, and 12 of the Fair Labor Standards Act, as
amended, and of regulations and orders of the United States Department of Labor
under Section 14 thereof.”
TABLE OF CONTENTS
DESCRIPTION AND PURPOSE ....................................................................................................................... 1
1. Purpose and Scope of Manual ................................................................................................................... 1
2. Purpose of Equipment ................................................................................................................................ 1
3. Leading Particulars..................................................................................................................................... 2
3.1
Leading Particulars: General .................................................................................................................. 2
3.2
PC-800 Series Signal Conditioner .......................................................................................................... 2
3.14 PC910 / 920 Conditioning Unit................................................................................................................ 5
3.14.1 Flow Sensor Input ............................................................................................................................... 5
3.14.2 Temperature Sensor Input .................................................................................................................. 5
3.14.3 Remote Input....................................................................................................................................... 5
3.14.4 Totalizer Output................................................................................................................................... 5
3.14.5 Remote Output .................................................................................................................................... 5
3.14.7 Auxiliary Rate Outputs......................................................................................................................... 5
3.14.8 Power Requirements........................................................................................................................... 6
3.14.9 Temperature Range ............................................................................................................................ 6
5. AT-205 and AT-206 (Lighted) Series Fuel Remaining Totalizing Indicator ................................................... 9
6. AT-209 Fuel Remaining Totalizer and AT-210 Fuel Consumed Totalizer................................................... 10
7. AR-204A (unlighted) and AR-207, AR-209 (lighted) Series Fuel Rate Indicator ......................................... 12
8. AT-204 and AT-208 (lighted) Series Fuel Consumed Totalizing Indicator .................................................. 13
9. General Description ..................................................................................................................................... 14
10. Functional Description ............................................................................................................................... 15
10.5 PC-910 / 920 Conditioner Unit ................................................................................................................. 17
11. Operation ................................................................................................................................................... 18
PREPARATION FOR USE .............................................................................................................................. 19
12. Unpacking and Inspection ......................................................................................................................... 19
13. Storage Instructions ................................................................................................................................... 19
14. Repacking for Shipment ............................................................................................................................ 19
INSTALLATION ............................................................................................................................................... 20
15. Turbine Flow/Temperature Transmitter ..................................................................................................... 20
16. Signal Conditioning Unit............................................................................................................................. 21
17. Flow Rate Indicator .................................................................................................................................... 21
18. Totalizing Indicator (Fuel Consumed)........................................................................................................ 21
19. Totalizing Indicator (Fuel Remaining) ........................................................................................................ 21
20. Interconnection Wiring ............................................................................................................................... 21
21. Magnetic Shield ......................................................................................................................................... 22
TESTING ......................................................................................................................................................... 24
23. Test Equipment Required For Testing....................................................................................................... 24
24. Description and Use of the PC-89 ............................................................................................................. 24
25. Test Procedure .......................................................................................................................................... 24
28. Calculating Ro and To Values..................................................................................................................... 26
INSTALLATION OF PC910 / 920 CONDITIONER UNIT ................................................................................ 26
TROUBLESHOOTING..................................................................................................................................... 30
MAINTENANCE............................................................................................................................................... 33
30. PC-800 Signal Conditioner ........................................................................................................................ 33
31. Flow Rate Indicator, AR-204A, AR-207 and AR-209 ................................................................................. 33
32. Totalizing Indicator, Fuel Consumed Totalizer, AT-204, AT-208 and AT-210 Series Models ................... 33
34. Turbine Flow Transmitter........................................................................................................................... 33
LIST OF FIGURES
Figure 1 Typical Units of the Fuel Management Systems ................................................................................. 1
Figure 2 Fuel Management Systems Block Diagram ...................................................................................... 15
Figure 3 Turbine Flow Transmitter Calibration Curve...................................................................................... 16
Figure 4 PC-910 / 920 Conditioner Block Diagram.......................................................................................... 17
Figure 5. PC910 Wiring Diagram for Single Engine Systems ......................................................................... 27
Figure 6. PC920 Wiring Diagram for Twin Engine Systems............................................................................ 28
Figure 7. PC810 TO PC910 Conversion Wiring Diagram ............................................................................... 29
Figure 8 PC-89 Precision Oscillator................................................................................................................. 36
LIST OF TABLES
Table 1 Troubleshooting .................................................................................................................................. 30
LIST OF DRAWINGS
3.11PC-800 Connector Wiring .......................................................................................................................... 3
3.12PC-820 Outline Drawing ............................................................................................................................. 4
4.9 81-300 Series Flow Transmitter Outline Drawing ....................................................................................... 8
5.6 AT-205 Outline Drawing............................................................................................................................... 9
5.7 AT-206 Outline Drawing............................................................................................................................... 9
5.8 Mounting Clamp -- Senior Aerospace Ketema. Part No. A2029SW......................................................... 10
6.8 AT-209 and AT-210 Outline Drawing......................................................................................................... 11
6.9 Mounting Clamp -- Senior Aerospace Ketema Part No. A2029ST............................................................ 11
7.9 AR-207 Outline Drawing ............................................................................................................................ 12
7.10 AR-204 Outline Drawing .......................................................................................................................... 12
7.11 AR-209 Outline Drawing .......................................................................................................................... 13
7.12 Mounting Clamp -- Senior Aerospace Ketema Part No. A2029ST.......................................................... 13
8.8 AT-204 Outline Drawing............................................................................................................................. 14
8.9 AT-208 Outline Drawing............................................................................................................................. 14
21.2 1/2-X-81-3XX Magnetic Shield Outline and Assembly Drawing ............................................................. 23
22.1 5/8-X-81-3XX Magnetic Shield Outline Drawing..................................................................................... 23
SC12 Series System
DESCRIPTION AND PURPOSE
1.
Purpose and Scope of Manual
This manual provides installation and maintenance instructions on the SC12 Series Senior
Aerospace Ketema Fuel Management Systems. It includes information on operations,
testing and troubleshooting a system. Typical system components are illustrated in Figure
1.
2.
Purpose of Equipment
The SC12 Series Senior Aerospace Ketema Fuel Management Systems precisely
measure and display the rate at which the fuel is being consumed by the aircraft. The
systems also compute and display the total fuel consumed (or remaining).
Figure 1 Typical Units of the Fuel Management Systems
TOTALIZERS
SIGNAL CONDITIONING UNIT
TURBINE FLOW / TEMPERATURE
TRANSMITTER
RATE INDICATOR
Page 1
Rev E 10-2000
This manual contains proprietary information which shall not be duplicated or used in whole or part without the
written permission from Senior Aerospace Ketema.
SC12 Series System
3.
Leading Particulars
A list of the significant electrical and physical specifications of the units of the Fuel
Management Systems is provided below.
3.1
Leading Particulars: General
Environmental Characteristics: The Fuel Management Systems are designed to conform
to the environmental requirements of FAA Document TSO-C44a and or TSO-C44b.
3.2
PC-800 Series Signal Conditioner
(All Systems unless otherwise specified on system drawing)
3.3
Analog Rate Output:
(Specifications are identical for each channel of each model.)
Type: Current
Full Scale Amplitude: 500 microamps
Impedance: 100k ohms minimum
Full Scale Range: 240 to 1010 Hz
Time Constant: Determined by rate indicator (=3 sec.)
Reference: Positive power supply terminal
Repeatability: ±0.2% of full scale
Linearity: ± 0.2% of full scale
Temperature Drift: ±0.2% of full scale/° F (±0.03% of full scale/° C)
Accuracy: ±1.1% of full scale
3.4
Input:
(Specifications are identical for each channel of each model.) Frequency Input:
Type: Balanced
Impedance: Greater than 20k ohms
Sensitivity: 7 millivolts RMS at frequencies less than 100 Hz
Frequency Range: 10 to 1 KHz
Temperature Input:
Type: Resistance/Temperature Sensor
Impedance: 1000 ohms ±1% @ 25° C
Temperature Coefficient: 6 ohms/° C
Temperature Range: -67° F to +158° F (-55° to +70° C)
3.5
Shock:
50G, 8 milliseconds
Page 2
Rev E 10-2000
SC12 Series System
3.6
Temperature Limits:
-22 to +122° F (-30 to +50° C)
3.7
Totalizer output:
Amplitude: Switch closure to ground less than 2 volt drop
Impedance: 10 ohms maximum
Polarity: Negative
Return: Positive of power supply
Pulse Width: 150 ± 30 ms
Rise Time: 25 microseconds maximum
Load Current: 450 mA maximum
Output Frequency:
PC-810: Equal to input frequency divided by division factor, 3 Hz maximum
PC-820: Equal to sum of two input frequencies divided by the division factor, 3 Hz
maximum
Accuracy: ± 1.2% of full scale
3.8
Power Requirements:
Voltage: 19 to 32 Vdc
Current: *
PC-810 Series: 100 mA maximum
PC-820 Series: 200 mA maximum
*Does not include totalizer current
3.9
Case:
Aluminum, Yellow Paint, per FED.STD. Color Number 23538
3.10
Weight:
1.2 lb. (0.54 kgm) PC-820
1.0 lb. (0.45 kgm) PC-810
3.11
PC-800 Connector Wiring
Page 3
Rev E 10-2000
SC12 Series System
3.12
PC-820 Outline Drawing
3.13
Page 4
Rev E 10-2000
SC12 Series System
3.14
PC910 / 920 Conditioning Unit
3.14.1
Flow Sensor Input
Input Full Scale Frequency Range: 240 to 1500 Hz
Input Type: Balanced
Input Impedance: 20K ohms
Input Sensitivity: 7 millivolts RMS at frequencies less than 100 Hz
Temperature Sensor Input
Temperature Sensor Type: RTD, Nickel 270 Alloy
Temperature Sensor Resistance @ 25°C: 1000 ohms 1% Temperature Coefficient:
6 % per °C
Temperature Range: -67°to 158° F (-55° to 70° C)
3.14.2
3.14.3
Remote Input
Frequency Range: 0 to 100 Hz
Input Type: 5V CMOS level compatible
Input Pulse Width: 10 ms
3.14.4
Totalizer Output
Output type: Solid-state switch to ground
Current sink: 400 mA maximum
Totalizer Supply Source: +28 vdc fuse protected
Pulse Width: 50 ms
Rise/fall time: < 25,us
Output Frequency: Dependent on scaling, 10 Hz maximum
Accuracy: ±3% of indicated total with fuel at nominal density. Variations in fuel
density from nominal will affect accuracy.
3.14.5
Remote Output
Frequency Range: 0 to 50 Hz
Output Type: Solid-state switch to ground with 5.1 K pull-up resistor to +5 vdc.
Output Amplitude: 5V
Pulse Width: 10 ms
Rise/fall Time: < 25 us
K-factor: 8 pulses per totalizer unit (0.1 or 1 EGU dependent on scaling).
3.14.6
Indicator Rate Output
Accuracy: ±3% of full scale flow rate with fuel of nominal density. Fuel density
variations from nominal will affect accuracy.
Linearity: ±1% of full scale
Repeatability: ±1% of full scale
3.14.7
Auxiliary Rate Outputs
Page 5
Rev E 10-2000
SC12 Series System
3.14.7.1 Auxiliary Rate Indicator Output
The Auxiliary Rate Indicator Output does not correct for indicator non-linearity.
The external rate indicator should be linear within ±1%. Refer to section 4.6 for
specifications.
3.14.7.2 Auxiliary Analog Output
Type: Voltage output signal proportional to flow rate
Full Scale Voltage: 5 vdc (Units with 0-5.333 vdc output are scaled so that the
output will be 5.00 vdc at a flow rate of 750 lb/hr regardless of the full scale flow
rate on the meter.)
Slew Rate: < 0.5 s from zero to full scale
Accuracy: ± 2.0% of full scale
Repeatability: ±0.1% of full scale
Linearity: ±0.5% of full scale
Temperature Drift: ±0.01 % of full scale per °F (± 0.02% of full scale per °C)
3.14.8
Power Requirements
Voltage: +19 to 32 vdc
Current: 75 mA typical, 100 mA maximum, excluding totalizer current
3.14.9
Temperature Range
-22° to +122° F
-30°to +50° C
Page 6
Rev E 10-2000
SC12 Series System
3.15
3.16
Page 7
Rev E 10-2000
SC12 Series System
4. 81-300 Series Flow Transmitter
4.1 Accuracy: ± 0.9% at cruise flow rate with a specific fuel.
4.2 Output: 28 mv minimum peak to peak at minimum linear flow rate.
4.3 Pressure Rating: 1500 PSI
4.4 Pressure Drop: not to exceed 6 PSI with locked element at max flow.
4.5 Temperature Limits: -67 to 158° F (-55 to 70° C)
4.6 Material: Stainless steel where exposed to fuel.
4.7 Linear Flow Rate:
1/2-2-81-301 100 to 850 pounds per hour
5/8-81-304
400 to 4000 pounds per hour
3/4-81-305
500 to 7000 pounds per hour
4.9 81-300 Series Flow Transmitter Outline Drawing
DIM
A
B
C
D
E
F
G
H
J
WEIGHT
1/2-2-81-301,306
2.32 MAX
1.00 SQ
1.22
2.45
0.312
0.625
0.3125 ID
MS33656-E8
8-32UNC-2B
Threaded 0.31
Deep
0.5 lb, 0.23 kg
1/2-1-81-302
2.32 MAX
1.00 SQ
1.22
2.45
0.312
0.625
0.3594 ID
MS33656-E8
8-32UNC-2B
Threaded 0.31
Deep
0.5 lb, 0.23 kg
5/8-1-81-303
2.38 MAX
1.12 SQ
1.35
2.70
0.375
0.750
0.3907 ID
MS33656-E10
8-32UNC-2B
Threaded 0.31
Deep
0.7 lb, 0.32 kg
Page 8
5/8-81-304
2.38 MAX
1.12 SQ
1.35
2.70
0.375
0.750
0.4687 ID
MS33656-E10
8-31 UNC-2B
Threaded 0.31
Deep
0.7 lb, 0.32 kg
3/4-81-305
2.63 MAX
1.37 SQ
1.62
3.25
0.500
1.000
0.5938 ID
MS33656-E12
10-32UNC-2B
Threaded 0.37
Deep
1.0 lb, 0.45 kg
Rev E 10-2000
SC12 Series System
5. AT-205 and AT-206 (Lighted) Series Fuel Remaining Totalizing Indicator
5.1 Input Amplitude + 24V ±10% pulse at 85 ±10 millisecond duration
5.2 Temperature Range: -22° to + 122° F (-30° to + 50° C), operating
5.3 Impedance: 10k ohms
5.4 Frequency Range: 0 to 6 Hz
5.5 Weight: AT-204 4 digits .80 lb. (.36 kgm)
5.6 AT-205 Outline Drawing
Page 9
Rev E 10-2000
SC12 Series System
5.8 Mounting Clamp -- Senior Aerospace Ketema. Part No. A2029SW
6. AT-209 Fuel Remaining Totalizer and AT-210 Fuel Consumed Totalizer
6.1 Input Signal
Type: High level single ended DC coupled pulse, input protected by diode clamping
Amplitude: 4.6 - 28 Volts peak, referenced to system ground
Pulse Duration: 10 millisecond min.
Frequency range: 0-10 Hz
6.2 Display
Type: Backlit liquid crystal avionics grade
Legend: 4 digit with internally programmable decimal point and engineering units label.
(lbs, gal, or kgs)
6.3 AT-209 Setting
Initial count setting is accomplished by the use of two momentary push buttons (set
up/set down).
6.4 AT-210 Reset
Accomplished by pressing the reset button for approximately 3 seconds. This will
reset the counter to zero.
6.5 Power Requirements
Voltage: 12 to 32 Vdc, referenced to system ground.
Current: 5mA Maximum
Display Lighting: 0-5 VDC, 300mA
Optional: 0-28 VDC, 100mA
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SC12 Series System
6.6 Temperature Range
-22° F to 122° F (-30° C to 50° C), operating
6.7 Model Code
AT 2XX-XX-05-5vdc lighting
AT 2XX-XX-28-28vdc lighting
6.8 AT-209 and AT-210 Outline Drawing
6.9 Mounting Clamp -- Senior Aerospace Ketema Part No. A2029ST
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SC12 Series System
7. AR-204A (unlighted) and AR-207, AR-209 (lighted) Series Fuel Rate Indicator
Movement: 250 degrees
Full Scale Deflection: 500 microamps dc
Accuracy: ±1 % of full scale
Resistance: 425 ohms maximum
Temperature Range: -22° to +122° F (-30° to 50° C) operating
Weight (maximum): 0.60 lb (.27 kgm)
Scale: Per sales order
Characters: Matte white Background: Flat black
7.8 Case: Per MS33639
7.1
7.2
7.3
7.4
7.5
7.6
7.7
7.9 AR-207 Outline Drawing
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SC12 Series System
7.12 Mounting Clamp -- Senior Aerospace Ketema Part No. A2029ST
8. AT-204 and AT-208 (lighted) Series Fuel Consumed Totalizing Indicator
8.1 Input Amplitude: + 26.4V ±15% pulse at 25 mSec duration
8.2 Temperature Range: -22° to +122° F (-30° to + 50° C), operating
8.3 Impedance: 120 ohms minimum
8.4 Frequency Range: 0 - 6 Hz
8.5 Weight:
AT-204:
4 digits 0.3 lb (0. 14 Kgm)
6 digits 0.4 lb (0.18 Kgm)
AT-208:
0.4 lb (0. 18 Kgm)
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SC12 Series System
8.6 AT-204 Rear Connector Wiring
8.7 AT-208 Rear Connector Wiring
9. General Description
9.1 Senior Aerospace Ketema Fuel Management Systems using a PC-800 or PC900
Series Signal Conditioner and a 81-300 Series Turbine Flow/Temperature Transmitter
(Figure 2) allow precise measurement of fuel flow with outputs proportional to flow rate.
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SC12 Series System
9.2 Fuel flowrate indication is provided for single or dual engine application on panel
mounted instruments. Panel display of total fuel consumed or remaining, as described, is
optional.
9.3 System Components
The systems are composed of the following components:
81-300 Series Turbine Flow/Temperature Transmitter - one per engine
PC-800 Series Signal Conditioning Unit (does not provide analog output to FMS)
PC-900 Series Signal Conditioning Unit (used to provide an analog output to FMS)
AR-200 Series Flow Rate Indicators -one per engine
AT-200 Series Fuel Consumed or Remaining Totalizer - optional
Figure 2 Fuel Management Systems Block Diagram
10. Functional Description
10.1 Turbine Flow/Temperature Transmitters
The turbine flow/temperature transmitter contains a turbine rotor which rotates at a speed
proportional to the volume of fuel passing through it. The turbine rotor produces a
sinusoidal voltage in a magnetic pickup coil installed in the body of the transmitter.
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SC12 Series System
This signal frequency is directly proportional to the volume of fuel flow. A temperature
sensor mounted in the body of the transmitter senses the temperature of the fuel passing
through it and transmits a variable resistance output signal to the signal conditioning unit.
The transmitter is calibrated to yield a fixed K-factor over a normal operating range with
minimum deviation at the cruise point of the aircraft (see Figure 3).
Figure 3 Turbine Flow Transmitter Calibration Curve
10.2 Signal Conditioning Unit
The signal conditioning unit differs in each of the two Fuel Management Systems. The
differences are explained in paragraphs 10.3 and 10.4.
10.3 PC-810 Series Signal Conditioner
This signal conditioner computes the fuel flow rate and total fuel consumed. The
computation is based on volume flow and fuel temperature yielding a mass flow when
scaled for a given fuel type.
The rate signal is produced by gating the analog sum of a reference voltage and
temperature converter voltage with a fixed width pulse. This signal drives a V/I Converter
which drives the rate indicator.
The compensated rate signal circuit also provides an analog signal to an ICO (Current
Control Oscillator). The ICO drives a binary divider which drives the totalizer through a
buffer.
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SC12 Series System
10.4 PC-820 Series Signal Conditioner
This signal conditioner contains two rate indicator and power supply circuits, each of which
functions identically to the rate indicator circuit of the PC-810 Signal Conditioner.
The two rate signals of this signal conditioner are summed to provide an analog signal to
the ICO.
10.5 PC-910 / 920 Conditioner Unit
After reset, the microcontroller reads a fixed memory contained within the analog
rate display and the switch settings on the CPU card. This information allows the
microcontroller to determine the correct engineering units, the full scale value of the
analog rate display, the model of turbine meter used, fuel type, and the resolution
of the totals information. This information along with basic system information is
resolved into two variables. The first is the theoretical fractional EGU amount of
fuel per turbine meter pulse at -60 Celsius known as the 'base'. The second is the
decrease in density of the fuel per RTD count per turbine meter pulse known as the
gain. These two variables are maintained in RAM memory and used by the 40
millisecond task to calculate the fuel flow rate.
Figure 4 PC-910 / 920 Conditioner Block Diagram
Each pulse from the turbine meter results in an interrupt to the microcontroller. The
interrupt firmware increments a memory location, used as a turbine meter pulse
accumulator, once for each interrupt.
An internal interrupt occurs each 10 milliseconds (msec). This interrupt is used to
establish the shape of the remote totalization output pulse, read and reset the
turbine meter pulse accumulator, read and reset the RTD input counter, schedule
the flow rate computation, and schedule the total pulse output check. If the remote
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SC12 Series System
total output counter is non-zero, a 40 msec, 50% duty cycle pulse is generated on
the remote total output.
The remote totals input also results in an interrupt. As with the turbine meter pulse,
this interrupt firmware also increments a memory location (the remote total output
counter) to record that the input has occurred.
Each 40 msec, the flow computation is performed. The turbine meter counts from
the current 40 msec interval are summed with the counts from the previous 19
intervals and multiplied by the base. Likewise, the product of the turbine meter
counts and RTD counts, in this interval, are summed with the products of the
previous nineteen intervals and multiplied by the gain. The gain result is subtracted
from the base result to give the appropriate engineering units flow rate as a percent
of full scale flow. This value is then used to set the 0 to 5 volt output
proportionately. The result is then further adjusted to provide a 0 to 500 uA output
current used to drive the analog rate display meter. The final function of this task is
to determine if a sufficient amount of fuel has been consumed to output a remote
totalization pulse. If this is the case, the remote total output counter is
incremented.
Each 50 msec the primary totalization task is executed. Its purpose is to determine
if eight remote output pulses have occurred and, if so, to output a totals pulse.
10.6 Fuel Flow Rate Indicator
The fuel flowrate indicator is a dc microammeter with an accuracy of ±1 %fullscale. The
scale of the indicator readout may be in pounds, gallons, kilograms or liters per unit time,
depending on the scaling requirement of the system.
10.7 Totalizing Indicator
Fuel flow systems are supplied with one of two types of totalizing indicator; one type
indicates fuel consumed and the other fuel remaining. The scales on both types of
indicators read out in pounds, gallons, kilograms or liters, depending on the scaling
requirements of the system.
10.8 The fuel consumed indicator has a reset (option) used to set the indicator to zero
when the fuel is loaded. As the fuel is consumed, the quantity is displayed on the
indicator.
10.9 The fuel remaining indicator has preset switches which allow the pilot to manually set
in the amount of fuel loaded in the aircraft. As fuel is consumed, the indicator subtracts
the amount from the preset value.
11. Operation
11.1 Indicators
The operation, or use of the rate indicator(s), requires only the observation of the engine
fuel flow rate indicator(s).
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SC12 Series System
11.2 Fuel Consumed Totalizing Indicator
After the fuel is loaded, perform the following:
Move the reset button guard away from the reset button on model AT-204 and AT-208.
Press the reset button until all digits read zero.
On Model AT-204 and AT-208, place reset guard in position to prevent accidental
resetting of the indicator during operation.
11.3 Fuel Remaining Totalizing Indicator
After fuel is loaded, perform the following:
If used, set the TOTAL PRESET switch at OPERATE (AT-205 and AT-206).
Press preset switches on the front of the indicator until the digits indicate the total of
pounds, gallons, kilograms or liters, as applicable, loaded on the aircraft.
If used, set the TOTAL PRESET switch at INTERLOCK to prevent accidental
changing of the indicator during operation (AT-205 and AT-206).
PREPARATION FOR USE
This section contains information on unpacking or repacking and inspection of the
instruments before installation in the aircraft. For specific information on the system and
dimensions of the instruments, refer to the system specification drawing, back of manual.
12. Unpacking and Inspection
Unpack the system components and inspect for physical damage, such as broken
indicator glass, dented cases, etc. If there is any apparent damage, file a claim with the
carrier.
13. Storage Instructions
Store the components of the Fuel Management System in their original shipping
containers in a dry area with temperature 13° C (55° F) to 35° C (95° F), if they are not to
be installed immediately.
Components of the SC12 System are shipped from Senior Aerospace Ketema in clear
moisture proof/vapor proof bags with desiccant and a moisture indicator card. It is
recommended that this equipment be stored in these heat sealed bags.
The shelf-life of the system components is 5 years with proper packaging.
14. Repacking for Shipment
The following steps are a general guide for repacking units for shipment.
NOTE: If units are to be shipped to Senior Aerospace Ketema attach a tag to each unit
identifying the owner and service or repair required.
If possible, use original shipping containers.
Wrap each unit in heavy paper or plastic before placing in shipping container.
Place packing material around each unit until there is no free space.
Seal the container using heavy tape.
Mark the container with suitable "handle with care" type cautions.
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SC12 Series System
INSTALLATION
This section contains installation instructions for the SC12 Fuel Management Systems.
The system drawing located in the back of this document contains the wiring
interconnections between the instruments and the dimensions for the required mounting
holes.
15. Turbine Flow/Temperature Transmitter
CAUTION: The flow/temperature transmitter must be installed with the arrow on the case
pointing in the direction of fuel flow. Failure to observe this caution will result in loss of
system accuracy.
15.1 Some engine manufacturers have made provisions for the installation of a fuel flow
transmitter in their engine fuel line by installing a spool piece. If a spool piece has been
installed in the engine fuel line for this purpose, remove the spool piece and replace it with
the transmitter.
15.2 If the engine manufacturer did not install a spool piece in the fuel line, the installor
will have to select a location in the engine fuel line to install the flow transmitter or contact
the engine manufacturer for their recommendations. Installing the flow transmitter in the
fuel line will result in some pressure drop; however, the Senior Aerospace Ketema flow
transmitter has been designed to minimize this pressure drop. The maximum pressure
drop which will result from installing the flow transmitter in the fuel line, locked rotor
pressure drop is shown on page 4.
15.3 Normally the best location in the fuel line to install the flow transmitter is downstream
from a fuel filter and the high pressure engine driven fuel pump, if space is available. The
location selected should also be downstream from any fuel system accessories or fuel
lines which may bypass a portion of the fuel and result in some of the fuel passing through
the flow transmitter a second time. Fuel passing through the flow transmitter twice will
result in an erroneous reading on the totalizing indicator.
15.4 If space is not available downstream from the high pressure engine driven fuel pump
to install the flow transmitter, a location should be selected downstream from a fuel filter
and the low pressure engine driven fuel pump. If the aircraft is not equipped with a low
pressure pump, then the flow transmitter should be installed downstream from a fuel
booster pump. The flow transmitter should always be located where the fuel line pressure
is a minimum of 15 psi greater than the vapor pressure of the fuel at the maximum fuel
temperature.
15.5 After the location for the transmitter has been selected, install the transmitter using
mating AN894 bushing, AN818 nuts and AN819 sleeves and reducers as required. To
complete the flow transmitter installation, it may be necessary to provide structural support
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SC12 Series System
for the transmitter. The four threaded holes located on the bottom of transmitter housing
can be used to secure the transmitter to a support bracket fabricated by the installor.
15.6 If Magnetic Shield(s) has been included as part of the fuel system kit to eliminate AC
interference, see pages 18 and 19 for installation procedures.
16. Signal Conditioning Unit
CAUTION: The signal conditioner should not be mounted in the engine compartment or
the engine accessory compartment. The unit should be mounted in a temperature
controlled area where the temperature will not exceed 50° C or fall below -30° C.
After a location has been selected which meets the above restrictions, drill four (4)
mounting holes as shown on the system drawing and secure the unit with four (4) bolts.
Make sure to allow room for the mating connectors which will be installed later.
17. Flow Rate Indicator
Select a convenient location on the instrument panel and drill mounting holes for the
indicator(s) and the two mounting clamp screws as shown in the system drawing. Mount
unit using Senior Aerospace Ketema panel clamp, part number A2029ST. Be sure to
allow room for the mating connector which will be installed later.
18. Totalizing Indicator (Fuel Consumed)
Select a convenient location on the instrument panel and drill a cutout and screw holes to
mount totalizer as shown on the system drawing and mount unit. Mounting an AT210
Totalizer requires Senior Aerospace Ketema panel clamp part number A2029SW. No
mating connector is used on the AT-204 Series Totalizer, however, when an AT-208 or
AT-210 Series Totalizer is used in a system, room should be allowed for a mating
connector which will be installed later.
19. Totalizing Indicator (Fuel Remaining)
Select a convenient location on the instrument panel and drill mounting holes for the
indicator and the two mounting clamp screws as shown on the system drawing. Mount
unit using Senior Aerospace Ketema part number A2029SW. Be sure to allow room for
the mating connector which will be installed later.
If a preset interlock switch is to be used (supplied by customer), select a location and drill
mounting hole and mount.
20. Interconnection Wiring
20.1 Using the supplied mating connectors, fabricate the interconnection cables (wire
supplied by customer). Refer to the system drawing in the back of this document for the
appropriate pin connections.
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SC12 Series System
20.2 Wiring to pins A and B of the flow/temperature transmitter(s) should be 20 or 22
AWG or equivalent twisted pair stranded shielded wire. Wiring to pins C and D of the
transmitter should be 20 or 22 AWG (or equivalent) stranded wire. If more convenient, the
installers may use a 4 wire shielded cable. Shields should be grounded only at the signal
conditioning unit as shown on the system drawing.
20.3 Wiring from the signal conditioning unit to the rate indicator(s) and totalizing indicator
should be 20 or 22 AWG (or equivalent) stranded wire. A 2 amp fast blow fuse or trip free
breaker should be installed between the signal conditioning unit and the 28 Vdc power
source.
20.4 Install the cable assembly in the aircraft and secure with appropriate cable clamps.
20.5 Connect the mating connector J1 to the Signal Conditioning Unit.
20.6 Connect the appropriate mating connector(s) to the flow transmitter(s) as shown on
the system drawing.
20.7 Connect the appropriate mating connector(s) to rate and totalizing indicator(s) as
shown on the system drawing. (NOTE: AT-204 Series Totalizing Indicator does not use a
mating connector. Dress the wires and make connection to the totalizer terminal block
pins A and B, see page 11.)
20.8 If preset interlock switch is to be used (Fuel Remaining Totalizer only), make
connection as shown on system drawing. The function of the preset interlock switch is to
disable the preset switches located on the front of the indicator preventing unauthorized
personnel from presetting a new fuel total without the pilot's knowledge. Perform onaircraft test procedure to verify proper installation.
21. Magnetic Shield
21.1 Installation Instructions -1/2-X-81-3XX Turbine Flowmeters
Place the top half of the shield over the pick-up coil of the flowmeter. Before installing the
bottom half of the shield over the flowmeter, align the flow arrows of the data labels of the
shield and the flowmeter in the same direction. This will prevent installing the flowmeter in
the fuel line in the reverse direction of fuel flow, which would result in an incorrect flow
measurement.
Slide the bottom half of the shield over the runners of the top half until the four holes in the
bottom of the shield align with the four holes in the bottom of the flowmeter. Secure the
bottom shield with the washers and screws provided. Install the flowmeter in the fuel line
after safety wiring the screws.
CAUTION: Using excess force, such as hammering or bending the bottom half of the
shield during installation will greatly reduce the magnetic shielding effect of the shield .
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SC12 Series System
21.2 1/2-X-81-3XX Magnetic Shield Outline and Assembly Drawing
22. Installation Instructions -5/8-X-81-3XX Turbine Flowmeters
The turbine meter should be installed in the fuel line per steps 15.1 through 15.5. Align the
flow arrow on the data label of the shield and the flow meter in the same direction.
Position the back half of the shield around the flowmeter until the two holes in the bottom
of the shield align with the two holes in the bottom of the flowmeter. Secure the back half
of the shield with washers and screws provided. Slide the front half of the shield over the
shield back half Secure the front half of the shield to the turbine meter at the remaining
two holes in the bottom of the turbine meter. Install the remaining two screws and
washers in the shield's side holes.
22.1 5/8-X-81-3XX Magnetic Shield Outline Drawing
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SC12 Series System
TESTING
This section contains on-aircraft test for the units of the Fuel Management System. The
on-aircraft test is used to check out the system after installation and as an aid when
troubleshooting a system.
23. Test Equipment Required For Testing
--Senior Aerospace Ketema Test Instrument, Model PC-89
--Stop Watch
24. Description and Use of the PC-89
The PC-89 illustrated on page 29 is a hand-held battery powered test instrument which
provides a precision pulse output signal which is substituted for the output signal of the
turbine flow transmitter during test. It is used for on-aircraft testing or troubleshooting of a
system without requiring engine(s) turn-up and provides the following system checks:
System wiring
Functional check of instrument units operating as a system (excluding turbine
transmitter).
Locating a faulty instrument unit of the system (excluding turbine transmitter).
Verifies scaling of signal conditioner.
25. Test Procedure
Calculate values for RO and TO (sample calculations found on page 22 of this section).
After calculating value for RO and TO, insert these values in space provided below. These
values will be used each time this system is checked:
RO = _________
TO = _________
25.1 Check the condition of the battery by activating its test switch. If green light glows,
PC-89 is ready for use. (Light cannot be seen in direct sunlight).
25.2 Remove the wire connector from one of the flow transmitters (if a twin engine
system) and connect it to the PC-89 output connector.
25.3 Turn frequency switch on PC-89 to Ft frequency value used to calculate RO and
switch on PC-89 power.
25.4 Place the temperature switch on the PC-89 to the REF. position.
25.5 Turn on aircraft 28 VDC power supply.
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SC12 Series System
26. Rate Indicator Check
26.1 The rate indicator should indicate the calculated RO value with ±2%.
26.2 If indicator does not indicate or indicates a value other than RO, refer to
Troubleshooting Table 3 on page 25 for possible cause of malfunction.
26.3 Check the compensating circuit of the signal conditioner by placing the temperature
switch on the PC-89 to the ELEV. position. The rate indicator RO value should indicate a
5% lower value than was indicated in step 15.10. If indication did not change in value, the
compensating circuit is not operating and the signal conditioner must be repaired. Return
temperature switch to REF. position before proceeding to step 27.
27. Totalizing Indicator Check
27.1 Start the stop watch just as the totalizer registers a count and record reading on
totalizer counter. Observe and record the time in seconds required for the totalizer to
indicate 10 counts. Time required for totalizer to indicate 10 counts should be within 10
times TO value ±3%.
27.2 If totalizer does not count or the time required for 10 counts does not equal 10 times
value of TO, refer to Troubleshooting Table 2, on page 24, for possible cause of
malfunction.
27.3 If system being checked is a twin engine system, disconnect PC-89 from first
transmitter cable connector and connect it to the other transmitter cable connector and
repeat Step 25.2 through 27.2 of this section.
27.4 If system checks out using the PC-89 test unit, turn up aircraft engine(s) and observe
if the system indicator(s) are operating.
27.5 If any of the indicators are not operating or are operating erratically, refer to
Troubleshooting Table 1 on page 23 for possible cause of malfunction.
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SC12 Series System
28. Calculating Ro and To Values
RO =
Ft × D
FS
TO =
3600
RO
Where:
Ft = Test frequency. The Ft frequency selected should be lower than the FS frequency
Fs = System full scale frequency setting. (located on system drawing and data label of
Signal Conditioner)
D = Full scale dial calibration (Rate Indicator dial)
RO = Dial reading, calculated
TO = Totalizer, seconds per count, calculated
28.1 Sample Calculation:
Assume FS = 523 Hz
Ft = 400 Hz,
RO =
Ft × D 400 X 600
=
= 459 ± 2%
FS
523
TO =
3600 3600
=
= 7.84 seconds ±3%
RO
459
D = 600 lbs/hr
INSTALLATION OF PC910 / 920 CONDITIONER UNIT
The PC910 and 920 Signal Conditioner Units provide the same function as the PC810
and 820 units, with the addition of an auxiliary analog voltage output. This output is
designed to provide an external flight management system with a temperature
compensated fuel flow-rate signal.
The PC910 / 920 Signal Conditioner was developed to be a replacement for PC810 /820
units and is housed in the same enclosure. The unit connectors are different, however,
and will require the aircraft harness to be re-terminated with the mating connectors
provided.
Each of the PC810 / 820 wires need to be re-terminated according to the diagram below.
Pins H and J are the additional connections necessary to provide the fuel flowrate signal
to the FMS input. AWG gauge 20 or 22 wire is recommended for all connections. Pin M
is the chassis connection and is normally connected to Pin P which is the 28 volt return.
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SC12 Series System
Figure 5. PC910 Wiring Diagram for Single Engine Systems
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SC12 Series System
Figure 6. PC920 Wiring Diagram for Twin Engine Systems
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Rev E 10-2000
SC12 Series System
Figure 7. PC810 TO PC910 Conversion Wiring Diagram
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Rev E 10-2000
SC12 Series System
TROUBLESHOOTING
29. This section provides information in locating and replacing faulty fuel system units.
After the faulty unit has been located, the unit should be replaced with a spare unit and
the faulty unit returned to Senior Aerospace Ketema for repair.
Table 1 Troubleshooting
SYMPTOM
Erratic indications
PROBABLE CAUSE
Signal Conditioner inputs
referenced to DC potential
Foreign material obstructing flow
transmitter rotor movement
Defective flow transmitter
bearings
Heavy vapor in fuel system
causing flow transmitter
deviations.
Low fuel pressure causing flow
transmitter deviations
No rate indication, totalizer Defective Rate Indicator
output is normal
Defective Signal Conditioner
Page 30
CORRECTIVE ACTION
Check input wiring for
correct connections and for
shorts to shielding; repair as
required. See paragraph
3.11, 20.2 and 34.7
Flush flow transmitter as
outlined in paragraph 34.3
Replace with spare unit and
return. faulty unit to Senior
Aerospace Ketema for
repair.
Rework or repair fuel
system.
Check fuel system
pressure; repair as required
return faulty unit to Senior
repair.
repair.
Rev E 10-2000
SC12 Series System
SYMPTOM
TotaIizer Inoperative
No flow rate or totaIizer
indication
PROBABLE CAUSE
Defective Totalizer AT-204
CORRECTIVE ACTION
Momentarily apply 28 VDC
across totalizer pins A and B. If
totalizer does not count each
time voltage is applied, totalizer
needs to be replaced. Return
defective totalizer to Senior
Aerospace Ketema for repair
Defective Totalizer AT-205 or
Apply 28 VDC to Pin A and the
AT-206
28 Vdc common to pin D.
CAUTION Reverse polarity will
damage the instrument.
Momentarily jumper Pin D to Pin
B. The totalizer should count
each time it is jumpered. If
totalizer does not count, it
should be replaced. Return
defective totalizer to Senior
Aerospace Ketema for repair.
Defective Wiring
Check wiring from Signal
Conditioning unit to totalizer.
See system drawing at end of
manual
Aerospace Ketema for repair.
Power not applied to Signal Check power connections, and
Conditioner.
fuse. See system drawing at
end of manual.
Foreign material obstructing
flow transmitter rotor
outlined in paragraph 34.4.
movement.
bearings.
Aerospace Ketema for repair
Flow transmitter coil or
Check coil, as required. Refer
temperature sensor defective
to paragraph 34.7.
Replace with spare unit. Return
faulty unit to Senior Aerospace
Ketema for repair.
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SC12 Series System
SYMPTOM
Flow indication with
engine(s) not in operation.
PROBABLE CAUSE
Defective ground
connections.
Strong AC interference.
Indicated flow less than
actual flow.
Foreign material obstructing
flow transmitter rotor
movement.
bearings.
Indicated flow suddenly
increases 20 percent with
no. change in engine power
setting.
Totalizer inoperative.
Temperature sensor in flow
transmitter shorted
Defective totalizer AT-210
Defective totalizer AT-209
Page 32
CORRECTIVE ACTION
Check ground connections;
correct as required.
Isolate interference source,
or reroute flow transmitter to
signal conditioner cable. If
interference persists, install
magnetic shield over flow
transmitter. See paragraph
21.
outlined in paragraph 34.4
repair.
Check pins C and D of flow
transmitter pick up coil.
Refer to paragraph 34.10.
Apply 28 Vdc to pin 2 and
the 28 Vdc common to pin
3. Push the reset switch.
The display should be all
zeros. Apply a 0 to 5V 1Hz
square wave to pin 1. The
display should count up at a
1Hz rate. If a malfunction is
detected the totalizer should
be replaced.
Apply 28 Vdc to pin 2 and
the 28 Vdc common to pin
3. Push the up/down set
switches for a display of
1000. Apply a 0 to 5 V 1Hz
square wave to pin 1. The
display should count down
at a 1 Hz rate. If a
malfunction is detected the
totalizer should be replaced.
Rev E 10-2000
SC12 Series System
MAINTENANCE
This section provides information on the maintenance requirements for the instrument
units of the Senior Aerospace Ketema Fuel Management systems.
30. PC-800 Signal Conditioner
No periodic maintenance of this instrument is required. If a malfunction occurs, the faulty
unit should be returned to Senior Aerospace Ketema.
A PC-800 Series Repair Manual and spare electronic board assemblies may be ordered
by customers located outside the U.S. when the instrument cannot be returned Senior
Aerospace Ketema for repair. Repairs on the instrument, however, should only be
attempted by a qualified technician.
31. Flow Rate Indicator, AR-204A, AR-207 and AR-209
No periodic maintenance of this instrument is required. If a malfunction occurs, the
instrument should be returned to Senior Aerospace Ketema for repair.
A repair manual for the AR-204A and AR-207 Series Model may be ordered by customers
located outside the U.S. when the instrument cannot be returned to Senior Aerospace
Ketema for repair. Repairs on the instrument, however, should only be attempted by a
qualified technician. No repair manual is available for the AR-209 Series Models; they
must be returned to Senior Aerospace Ketema for repair.
32. Totalizing Indicator, Fuel Consumed Totalizer, AT-204, AT-208 and AT-210 Series
Models
No periodic maintenance of these totalizing indicators is required. Should a malfunction
occur, the faulty unit must be replaced with a spare unit, as it is not repairable. If the
faulty unit still is under warranty, return it to Senior Aerospace Ketema for replacement.
33. Fuel Remaining Totalizer, AT-205, AT-206 and AT-209 Series Models No periodic
maintenance of these totalizing indicators is required. If a malfunction occurs, the faulty
unit should be returned to Senior Aerospace Ketema for repair.
A repair manual can be ordered by customers located outside the U.S. if the instrument
cannot be returned to Senior Aerospace Ketema for repair. Repairs on the instrument,
however, should only be attempted by a qualified technician.
34. Turbine Flow Transmitter
The recommended maintenance of this instrument consists of replacing the bearings and
shaft every 5000 hours and recalibration.
Page 33
Rev E 10-2000
SC12 Series System
Indication of bearing wear or failure is lower than normal, erratic or zero flow rate
indication.
When bearing replacement is required, the transmitter must be returned to Senior
Aerospace Ketema for replacement of bearings, shaft and recalibration.
34.1 Transmitter rotor failure may, on some occasions, be due to excessive dirt in the fuel.
Rotor operation can sometimes be restored by flushing. To flush rotor assembly, use the
following procedure:
34.2 Remove flow transmitter from fuel line, noting flow direction by arrow on case.
(Reinstall transmitter with arrow on case pointing in direction of fuel flows.)
CAUTION: DO NOT USE AIR HOSE TO SPIN ROTOR AS EXCESSIVE PRESSURE
WILL CAUSE ROTOR TO OVERSPEED, DAMAGING BEARINGS.
34.3 Blow lightly into the transmitter housing and observe rotor movement. (If the
transmitter is in good condition, the rotor will spin freely for several seconds.)
34.4 Flush transmitter with isopropyl alcohol.
34.5 Repeat step 34.4 if no improvement is observed; repeat step 34.3 as required.
34.6 If rotor does not spin freely after repeating steps 34.3 and 34.4, new bearings are
required and transmitter should be returned to Senior Aerospace Ketema for repair.
34.7 The flow transmitter pickup coil is manufactured to insure greatest possible life.
Failure is unusual, but may occur as a result of internal wire damage caused by thermal
effects. To test coil, use the following procedure:
34.8 Check resistance between pins A and B with an ohmmeter (normal resistance is
3100 ohms ±10% at 25° C). If the ohmmeter shows the pickup coil has failed by opening
or shorting, the flow transmitter must be returned to Senior Aerospace Ketema for repair.
34.9 Check resistance between pin A and turbine meter housing. The pickup coil must be
isolated from the housing by 20 Meg. ohms minimum.
34.10 Check the resistance between pins C and D with an ohmmeter (normal resistance is
1000 ohms ±2% at 25° C). If the ohmmeter shows the temperature sensor has failed by
opening or shorting, the flow transmitter must be returned to Senior Aerospace Ketema for
repair.
Page 34
Rev E 10-2000
SC12 Series System
NOTES:
Page 35
Rev E 10-2000
SC12 Series System
Figure 8 PC-89 Precision Oscillator
619-442-3451 or 619-588-3373
Fax 619-440-1456 or 619-588-3381
www.sfketema .com
©Senior Aerospace Ketema 1998, 1999, 2000, 2001
Printed in U.S.A.
Page 36
Rev E 10-2000

Fuel Management System SC12 SERIES

Transcription

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